Gas Turbine Vane Assembly for Leading Edge De-Icing

Resolve Bottlenecks,
Find Innovative SolutionsGenerate Solutions

Solution Overview

Problem

Conventional de-icing systems for gas turbine engine vanes suffer from inefficient heating of leading edges and aerodynamic losses due to the design of internal passageways, leading to ice build-up and potential damage from shed ice.

Innovation Solution

A vane assembly design that directs fluid flow through a leading edge passageway followed by trailing edge passageways, effectively heating the leading edge first and minimizing aerodynamic losses by exhausting fluid through the pressure surface.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Ease of manufacture

If a single internal passageway with long straight narrow passages is used to distribute bleed air, then the passages can be manufactured using conventional EDM methods, but the heating efficiency of the leading edge is reduced and aerodynamic losses increase

Engineering Contradiction:

Improvemanufacturability of passagesVSAvoidheating efficiency of leading edge

Core Design Contradiction:

Ease of manufactureVSUse of energy by moving object

Solution Approach 1:

The single internal passageway is segmented into multiple separate passageways. Each passageway is positioned to be in substantial proximity to a different region of the leading edge, allowing independent optimization of each passage's route and heating effectiveness while maintaining manufacturability

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

Each passageway is configured with local quality tailored to its specific location, with passages routed to deliver heated air precisely where needed on different leading edge regions, optimizing heat distribution across the entire leading edge surface

Inventive Principle:

Principle #3Local quality

2Temperature

If passages are routed close to the pressure surface, then heating effectiveness increases, but aerodynamic losses occur when exhaust air separates from the suction surface

Engineering Contradiction:

Improveheating effectiveness of aerofoil surfacesVSAvoidaerodynamic losses

Core Design Contradiction:

TemperatureVSLoss of energy

Solution Approach 1:

Instead of exhausting air through the suction surface as in conventional designs, the invention inverts the approach by routing passageways to exhaust air through or near the pressure surface, eliminating the aerodynamic separation problem while maintaining heating effectiveness

Inventive Principle:

Principle #13The other way round (Inversion)

3Temperature

If metering holes are positioned on the suction surface to get close to the pressure surface, then heating distribution improves, but aerodynamic performance deteriorates due to flow separation

Engineering Contradiction:

Improveheat distribution to pressure surfaceVSAvoidaerodynamic performance

Core Design Contradiction:

TemperatureVSProductivity

Solution Approach 1:

The invention inverts the conventional approach by positioning metering holes and exhaust outlets on the pressure surface rather than the suction surface, thereby eliminating flow separation and aerodynamic losses while achieving effective heat distribution to the pressure surface

Inventive Principle:

Principle #13The other way round (Inversion)

Applied Scientific Principles

This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.

Function Achieved in This Case

Enhances heating efficiency of the leading and pressure surfaces of the vane, reducing ice build-up and minimizing aerodynamic losses, while allowing for lighter and more fuel-efficient operation.

Implementation Method 1

Flow of the fluid through the plurality of trailing edge passageways may also heat the pressure surface of the aerofoil effectively

Methodology Applied

Scientific EffectConvection: Convection

Implementation Method 2

distribute heat more effectively to the desired portions of the aerofoil

Methodology Applied

Scientific EffectThermal conduction: Conduction (thermal)

Data Source

PatentEP4198269B1Vane assembly for a gas turbine engine

Publication Date: 2025.12.31 ROLLS ROYCE PLC

Figure 1
Figure 2
Figure 3

AI summary

A vane assembly (200) for a gas turbine engine (10). The vane assembly is a single unitary component that includes an aerofoil (202). The vane assembly further includes a leading edge passageway (230) disposed proximal to a leading edge (210) of the aerofoil and configured to receive a flow of a fluid (220) therein. The vane assembly further includes a connecting passageway (250) fluidly communicating the leading edge passageway with a trailing edge distribution passageway (240) that is spaced apart from the leading edge, the leading edge passageway (230) and a trailing edge (208) of the aerofoil. The vane assembly further includes a plurality of trailing edge passageways (260) disposed proximal to a pressure surface (212) of the aerofoil and extending from the trailing edge distribution passageway towards the trailing edge along a chordwise direction (C). Each of the plurality trailing edge passageways is configured to discharge the fluid through a corresponding passageway outlet (270) disposed on the pressure surface and in fluid communication with a corresponding trailing edge passageway.